Skip to Main content Skip to Navigation

Geometric Simplification for Radiative Thermal Simulation of satellites

Vincent Vadez 1, 2 
1 TITANE - Geometric Modeling of 3D Environments
CRISAM - Inria Sophia Antipolis - Méditerranée
Abstract : The life cycle of a satellite includes the launch phase, the positioning on the desired orbit, different maneuvers (e.g. deployment of solar panels and safety position), and finally placing the satellite on the junk orbit. The satellite gravitates in a hostile environment, exposed to thermal variations of very large amplitude, alternating sun exposure and eclipse phases. The survival of the satellite depends on the temperature of its components, the variation of which must be monitored within safety intervals. In this context, the thermal simulation of the satellite for its design is crucial to anticipate the reality of its operation. Radiative thermal simulation is essential for anticipating the generation of energy from solar and albedo radiation, and for regulating temperatures of on-board equipments. Ideal operation consists in providing appropriate cooling for components exposed to radiation, and conversely, heating of unexposed components. As an order of magnitude, the external temperature ranges from -150 to +150 degrees Celsius, and the internal electronic equipment has for instance a safe range between -50 and +50 degrees Celsius, with a safety margin of 10 degrees. In the eclipse phase where the radiation is significantly lower, heating is provided by the energy accumulated during the exposed phase, combined with heat pipes for thermal regulation. In this thesis, the objective is to advance the knowledge on radiative thermal simulation calculation methods for satellites. To this end, two approaches are considered. The first approach consists in establishing a reference calculation of a quantity governing radiative thermal simulation: view factors. Being subject to time constraints, this method is based on a hierarchical data structure enabling progressive computation of view factors, in order to offer a satisfactory tradeoff between time dedicated to computations and desired accuracy. For the sake of accuracy, a prediction step is added to guarantee a better convergence towards the reference value. The second approach, also motivated by time constraints, aims at reducing the geometric model of a mechanical part or a spacecraft while being faithful to the numerical simulation. In order to render the decimation physics-informed, a preprocessing step relying on a sensitivity analysis is carried out. To better preserve the physical simulation, the geometric cost of a simplification operator is coupled to a factor deduced from the simulation deviation between the reference model and the reduced model.
Document type :
Complete list of metadata
Contributor : Vincent Vadez Connect in order to contact the contributor
Submitted on : Tuesday, August 16, 2022 - 9:47:32 AM
Last modification on : Wednesday, August 17, 2022 - 3:30:19 AM


Files produced by the author(s)


  • HAL Id : tel-03751964, version 1



Vincent Vadez. Geometric Simplification for Radiative Thermal Simulation of satellites. Computer Science [cs]. Université cote d'azur, 2022. English. ⟨tel-03751964⟩



Record views


Files downloads